著者

苅田 丈士 片野 克哉 緒川 修治

出版者

一般社団法人 日本機械学会

雑誌

年次大会 2020 (ISSN:24242667)

巻号頁・発行日

pp.J19108, 2020 (Released:2021-03-25)

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Pulse detonation engine (PDE) performances were calculated. Simple relationships were derived for detonation, exhausting and ventilation to calculate the engine performances. Calculated Isp were about 20 km/s in subsonic flight and 5 km/s in supersonic flight, respectively. A spaceship with PDE and a rocket engine was conceptually designed, and its transportation performance was estimated with use of the extended Tsiolkovskii method. When the mass at take-off was 3,000 kg, 2,230 kg was carried to the altitude of 101 km.